Research on nonlinear aerodynamics modeling and dynamic response in icing conditions

Current flight dynamic researches are commonly based on linear aerodynamics and icing effect model. Researches on nonlinear aerodynamics modeling in icing conditions are relatively rare, however, nonlinear model is of great importance in flight dynamics analysis especially in high angle of attack regions. The paper proposes the linear aerodynamics model to a nonlinear aerodynamics model considering the icing effect in icing conditions. Corrections are presented to modify the aerodynamics parameters of stall and post-stall region based on the wind tunnel test results in a wide range of angles of attack. Dynamic response of different elevator impulse is investigated. Simulation results show that the proposed model can reflect the flight characteristics of the aircraft in icing conditions, and provides a theoretical support for nonlinear flight dynamic research in stall and post-stall region.